Тип публикации: статья из журнала
Год издания: 2002
Идентификатор DOI: 10.1023/A:1020401107010
Аннотация: The possibility of developing power and transport systems for space applications is examined. It is suggested to use an MHD generator utilizing inhomogeneous gas-plasma flows of inert gas as the source of electric energy in such systems. The plasma of the current layers may be in the state of "frozen ionization," when the degree ofПоказать полностьюionization exceeds the equilibrium level thereby providing for an effective MHD interaction with the enthalpy extraction coefficient of 0.4 and adiabatic efficiency of 0.8. Such a plasma is stable with respect to dissipative instabilities (ionization and overheating) and retains its positive properties at a stagnation pressure of the order of 1 MPa. The estimation of the mass-and-size characteristics of a closed-cycle solar MHD facility for space applications reveals that the specific power of the facility may amount to 500 W/kg. It is suggested that the propulsion unit should be provided by an electric rocket engine on the basis of an MHD accelerator, with the working medium provided by a nonuniform gas-plasma flow in which azimuthal plasma rings (T-layers) are inductively connected to the electric energy source. In a flow with T-layers, an efflux velocity of the order of 40 km/s is attained. With a mass flow rate of 50 g/s, the engine may develop a propulsive force of 2000 N.
Журнал: HIGH TEMPERATURE
Выпуск журнала: Vol. 40, Is. 5
Номера страниц: 754-768
ISSN журнала: 0018151X
Место издания: NEW YORK
Издатель: MAIK NAUKA/INTERPERIODICA